EP4034753B1 - Schaufel für ein strömungsmaschinentriebwerk und zugehöriges strömungsmaschinentriebwerk - Google Patents

Schaufel für ein strömungsmaschinentriebwerk und zugehöriges strömungsmaschinentriebwerk Download PDF

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Publication number
EP4034753B1
EP4034753B1 EP20776170.1A EP20776170A EP4034753B1 EP 4034753 B1 EP4034753 B1 EP 4034753B1 EP 20776170 A EP20776170 A EP 20776170A EP 4034753 B1 EP4034753 B1 EP 4034753B1
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EP
European Patent Office
Prior art keywords
blade
zone
platform
radial distance
protective strip
Prior art date
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Active
Application number
EP20776170.1A
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English (en)
French (fr)
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EP4034753A1 (de
Inventor
Pierre-Marie FONTS
Marc Maurice Dijoud
Hélène CLECH
Michel NIN
Lorenzo Huacan Hernandez
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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Publication of EP4034753A1 publication Critical patent/EP4034753A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the field of turbomachines, such as a gas turbine, for example of an aircraft.
  • the present invention relates to a blade for a turbomachine engine and a turbomachine engine.
  • the present invention relates to the protection of gas turbine blades against damage caused by oxidation and/or corrosion, and this, in particular in critical areas of the blade.
  • critical zone we mean a zone of the blade in which any damage can functionally impact the blade.
  • the most feared functional impact concerns the reduction in the life of the blade due to thermomechanical or vibratory fatigue caused by oxidation and corrosion in areas of the blade where the stresses are high.
  • the high stress zones are located in the root of the blade, close to the platform.
  • the complete profile of the blade can, for example, be coated entirely and homogeneously with a material having better resistance to oxidation and corrosion.
  • a material having better resistance to oxidation and corrosion reduces the creep life of the blade by adding mass at the head and in the middle of the profile.
  • the generalized increase in mass also increases the stresses in the lower part of the profile and reduces its resistance to thermomechanical or vibratory fatigue.
  • the coating at the top of the blade can also creep and create unwanted touches between rotor and stator.
  • EP 1 980 713 A2 discloses a blade for a turbomachinery engine according to the preamble of claim 1.
  • the object of the present invention is therefore to overcome the aforementioned drawbacks.
  • the objective of the invention is therefore to allow effective protection of a turbine engine blade against corrosion and oxidation, without impacting the performance of the engine.
  • the invention therefore relates to a blade for a turbomachine engine comprising an aerodynamic blade extending radially outwards and comprising a blade tip and a blade root, and a platform connected to the blade root by an upper end .
  • the maximum radial distance between the blade tip and the platform defines a maximum extent of the airfoil of the blade.
  • the blade is partially covered with a strip for protection against oxidation and corrosion, said strip extending between a lower limit located on at least part of the platform and an upper limit located on the blade root.
  • the protective strip covers the blade only at its highly stressed inner radial end.
  • the outer radial end of the blade, or blade head, is therefore not coated.
  • the nuisances linked to the presence of a coating on the outer radial end of the blade are avoided, in particular in terms of mass, increase in stresses, creep of the coating, etc., while improving the fatigue life and thermomechanical life of the inner radial end of the blade.
  • the radial distance between said limits defines the height of the protective strip.
  • the lower limit is located at a lower end of the platform, radially opposite the upper end.
  • the upper limit is located between a first radial distance and a second radial distance.
  • Said first radial distance corresponds to a distance between the connection of the blade root to the platform and a first zone located on said blade root
  • said second distance corresponds to a distance between the connection of the blade root to the platform and a second area located on said blade root.
  • Said second zone corresponds to a creep limiting zone.
  • “Creep-limiting” zone means a zone combining a mechanical stress and a thermal level such that the blade will deteriorate (or age) preferentially in creep in this zone. This zone is typically close to the middle of the profile.
  • the limiting creep zone can be determined, for example, by testing the component, or by elasto-plastic calculations over the entire blade to highlight the zones which would deform the most under the effect of stresses, temperatures and durations of application of these stresses, or for example, by the Larson-Miller relation binding over the entire blade stresses, temperatures and lifespans to rupture for a given material, the limiting zone in creep being, for example, the zone between once and twice the minimum lifetime.
  • the first radial distance is greater than or equal to 5mm.
  • the upper limit is located 5mm from the connection of the blade root to the platform.
  • the second radial distance is less than or equal to 50% of the maximum extent of the airfoil surface of the blade, for example less than or equal to 40% of the maximum extent of the airfoil surface of the blade.
  • the upper limit is located at a distance from the connection of the blade root to the platform less than or equal to 50% of the maximum extent of the lifting surface of the blade, for example less than or equal to 40% of the maximum extent of the airfoil of the blade.
  • the protective strip comprises at least one zone of constant coating thickness.
  • the protective strip comprises an upper transition zone extending radially between the part of uncoated blade and the protective strip area of constant coating thickness.
  • the protective strip is applied upstream of a deposition of a coating forming a thermal barrier.
  • the protective strip is preferably made of a material chosen at least from the group comprising aluminum, iron, nickel, cobalt, yttrium, rare earths or precious metals.
  • the invention relates to a turbomachine engine comprising a plurality of blades as described previously.
  • upstream and downstream are defined with respect to the direction of air circulation in the turbomachine.
  • inner and outer are defined with respect to a direction radial to the main longitudinal axis X-X of the blade, the inner being closer to the main axis than the outer.
  • FIG 1 very schematically shows a perspective view of a blade 10 designed to be mounted in a turbomachine (not shown), and in particular an aircraft turbojet.
  • the turbomachine will not be detailed in the remainder of the description.
  • the blade 10 comprises an aerodynamic blade 12 extending radially outwards, and comprising an outer radial end or blade tip 14 and an inner radial end 16 or blade root.
  • the blade 10 further comprises a platform 18 connected to the blade root 16 and a journal 20 able to engage, for example, in a bore of an element of the turbine engine.
  • the platform 18 is delimited by an upper end 18a connected to the blade root 16 and a lower end 18b, radially opposite to the upper end 18a and, for example, connected to the journal 20.
  • the maximum radial distance H between blade tip 14 and platform 18 defines the maximum radial height or extent of the airfoil of blade 12.
  • the blade 10 is partially covered with a strip 30 for protection against oxidation and corrosion.
  • the band 30 covers the vane 10 only at its highly stressed internal radial end.
  • the outer radial end 14 of the blade 12 is not coated.
  • the nuisances linked to the presence of a coating on the outer radial end of the blade are avoided, in particular in terms of mass, increase in stresses, creep of the coating, etc., while improving the fatigue life and thermomechanical life of the inner radial end of the blade.
  • the protective band 30 extends between a lower limit L1 and an upper limit L2.
  • the radial distance D between said limits L1, L2 defines the height of the strip 30 of protection.
  • the lower limit L1 is located on the platform 18, for example at its lower end 18b. Generally, the lower limit L1 is located on a part of the platform 18.
  • the upper limit L2 is located at the inner radial end 16 of the blade 12, for example on the blade root.
  • the upper limit L2 is located between a first radial distance d1, visible on the figure 1 and a second radial distance d2, visible on the figure 2 .
  • the first radial distance d1 corresponds to a distance between the connection of the blade root 16 to the platform 18 and a first zone Z1 located on the blade root 16.
  • the second radial distance d2 corresponds to a distance between the connection of the blade root 16 to the platform 18 and a second zone Z2 located on the blade root 16.
  • the second zone Z2 corresponds to a so-called “creep-limiting” zone.
  • “Creep-limiting” zone means a zone combining a mechanical stress and a thermal level such that the blade will deteriorate (or age) preferentially in creep in this zone.
  • This zone is conventionally close to the middle of the profile and can be determined for example by testing the component, or by elasto-plastic calculations over the entire blade to highlight the zones which would deform the most under the effect of stresses, temperatures and the durations of application of these stresses, or for example, by the Larson-Miller relationship linking stresses, temperatures and fracture life spans for a given material over the entire blade.
  • the limiting creep zone is, for example, the zone between once and twice the minimum service life.
  • the first radial distance d1 is greater than or equal to 5 mm and the second radial distance d2 is less than or equal to 50% of the maximum extent H of the bearing surface of the blade 12, for example less than or equal to 40% of the maximum extent H of the lifting surface of the blade 12.
  • the protective strip 30 comprises an upper transition zone T1, visible on the picture 3 , of variable coating thickness, extending between the blade part 12 devoid of coating and a lower zone T2 of the protective strip 30 of constant coating thickness.
  • the blade 10 can be made of a material based on nickel, cobalt, equiaxed-DS-monocrystal and can be obtained by a mass cutting process, casting, forging or by any other process.
  • the protective strip 30 may comprise aluminum with or without additives from precious metals or rare earths, for example MCrAIY, with M chosen from iron, nickel, cobalt, yttrium, or even rare earths. or precious metals.
  • the protective strip 30 can be applied upstream of a deposition of a coating forming a thermal barrier.
  • the strip for protection against corrosion and oxidation according to the invention minimises the lifetimes in thermomechanical or vibratory fatigue of the blades, and in particular of the blade roots, by eliminating the risk of initiating cracks at the root. blade by eliminating surface damage linked to oxidation and corrosion.
  • the protective strip covering the blade only at its inner end makes it possible to limit the functional impacts linked to the addition of an anti-oxidation coating.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Schaufel (10) für einen Turbomaschinenmotor, umfassend :
    - ein aerodynamisches Schaufelblatt (12), die sich radial zur Außenseite hin erstreckt und einen Schaufelblattkopf (14) und einen Schaufelblattfuß (16) umfasst, und
    - eine Plattform (18), die mit dem Schaufelblattfuß (16) durch ein oberes Ende (18a) verbunden ist, wobei der maximale radiale Abstand (H) zwischen dem Schaufelblattkopf (14) und der Plattform (18) eine maximale Erstreckung der tragenden Fläche des aerodynamischen Schaufelblatts (12) definiert, so dass die Schaufel (10) teilweise mit einem Schutzstreifen (30) gegen Oxidation und Korrosion bedeckt ist, wobei sich der Streifen (30) zwischen einer unteren Begrenzung (L1), die sich zumindest auf einem Teil der Plattform (18) befindet, und einer oberen Begrenzung (L2), die sich auf dem Schaufelblattfuß (16) befindet, erstreckt,
    dadurch gekennzeichnet, dass der Schaufelblattkopf (14) nicht mit dem Schutzstreifen (30) beschichtet ist.
  2. Schaufel (10) nach Anspruch 1, wobei die untere Begrenzung (L1) sich an einem unteren Ende (18b) der Plattform (18) radial gegenüber dem oberen Ende (18a) befindet.
  3. Schaufel (10) nach Anspruch 1 oder 2, wobei die obere Begrenzung (L2) sich zwischen einem ersten radialen Abstand (d1) und einem zweiten radialen Abstand (d2) befindet, wobei der erste radiale Abstand (d1) einem Abstand zwischen der Verbindung des Schaufelblattfußes (16) zur Plattform (18) und einer ersten Zone (Z1), die sich auf dem Schaufelblattfuß (16) befindet, entspricht und der zweite Abstand (d2) einem Abstand zwischen der Verbindung des Schaufelblattfußes (16) zur Plattform (18) und einer zweiten Zone (Z2), die sich auf dem Schaufelblattfuß (16) befindet, entspricht.
  4. Schaufel (10) nach Anspruch 3, wobei der erste radiale Abstand (d1) größer oder gleich 5 mm ist.
  5. Schaufel (10) nach Anspruch 3 oder 4, wobei der zweite radiale Abstand (d2) kleiner oder gleich 50 % der maximalen Erstreckung (H) der tragenden Fläche des aerodynamischen Schaufelblatts (12) ist.
  6. Schaufel (10) nach einem der vorhergehenden Ansprüche, wobei der Schutzstreifen (30) mindestens eine Zone (T2) mit konstanter Beschichtungsdicke umfasst.
  7. Schaufel (10) nach Anspruch 6, wobei der Schutzstreifen (30) eine obere Übergangszone (T1), die sich radial zwischen dem aerodynamischen Schaufelblattteil (12) ohne Beschichtung und der Zone (T2) des Schutzstreifens (30) mit konstanter Beschichtungsdicke erstreckt.
  8. Schaufel (10) nach einem der vorhergehenden Ansprüche, wobei der Schutzstreifen (30) stromaufwärts einer Abscheidung einer Beschichtung, die eine Wärmebarriere bildet, aufgebracht ist.
  9. Schaufel (10) nach einem der vorhergehenden Ansprüche, wobei der Schutzstreifen (30) aus einem Material hergestellt ist, das zumindest aus der Gruppe ausgewählt ist, die Aluminium, Eisen, Nickel, Kobalt, Yttrium, seltene Erden oder Metalle umfasst.
  10. Turbomaschinenmotor, umfassend eine Vielzahl von Schaufeln nach einem der vorhergehenden Ansprüche.
EP20776170.1A 2019-09-24 2020-09-23 Schaufel für ein strömungsmaschinentriebwerk und zugehöriges strömungsmaschinentriebwerk Active EP4034753B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1910503A FR3101108B1 (fr) 2019-09-24 2019-09-24 Aube, notamment de turbomachine, partiellement recouverte en pied d’aube d’une bande de protection contre l’oxydation et la corrosion
PCT/EP2020/076620 WO2021058599A1 (fr) 2019-09-24 2020-09-23 Aube pour un moteur de turbomachine et moteur de turbomachine associé

Publications (2)

Publication Number Publication Date
EP4034753A1 EP4034753A1 (de) 2022-08-03
EP4034753B1 true EP4034753B1 (de) 2023-07-12

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20776170.1A Active EP4034753B1 (de) 2019-09-24 2020-09-23 Schaufel für ein strömungsmaschinentriebwerk und zugehöriges strömungsmaschinentriebwerk

Country Status (4)

Country Link
EP (1) EP4034753B1 (de)
CN (1) CN114430788A (de)
FR (1) FR3101108B1 (de)
WO (1) WO2021058599A1 (de)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004023623A1 (de) * 2004-05-10 2005-12-01 Alstom Technology Ltd Strömungsmaschinenschaufel
US8708658B2 (en) * 2007-04-12 2014-04-29 United Technologies Corporation Local application of a protective coating on a shrouded gas turbine engine component
US20130230406A1 (en) * 2007-12-27 2013-09-05 Melvin Howard Wilkins Corrosion Resistant Articles
US8511993B2 (en) * 2009-08-14 2013-08-20 Alstom Technology Ltd. Application of dense vertically cracked and porous thermal barrier coating to a gas turbine component
US9587645B2 (en) * 2010-09-30 2017-03-07 Pratt & Whitney Canada Corp. Airfoil blade
US9506347B2 (en) * 2012-12-19 2016-11-29 Solar Turbines Incorporated Compressor blade for gas turbine engine
US9719371B2 (en) * 2012-12-20 2017-08-01 Siemens Aktiengesellschaft Vane segment for a gas turbine coated with a MCrAlY coating and TBC patches
US10408224B2 (en) * 2014-01-23 2019-09-10 United Technologies Corporation Fan blades with abrasive tips
US10174626B2 (en) * 2014-10-15 2019-01-08 Pratt & Whitney Canada Corp. Partially coated blade

Also Published As

Publication number Publication date
FR3101108A1 (fr) 2021-03-26
EP4034753A1 (de) 2022-08-03
WO2021058599A1 (fr) 2021-04-01
FR3101108B1 (fr) 2022-09-02
US20220341336A1 (en) 2022-10-27
CN114430788A (zh) 2022-05-03

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